XFOIL Version 6.96 Calculated polar for: GOE 234 (MVA CA5) AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.750 -0.1392 0.12921 0.12731 -0.0728 0.9374 0.0208 -12.500 -0.4304 0.06271 0.06030 -0.1094 0.9193 0.0236 -12.250 -0.4578 0.05470 0.05207 -0.1165 0.9026 0.0239 -11.750 -0.4454 0.04802 0.04520 -0.1244 0.8785 0.0244 -11.500 -0.4298 0.04512 0.04221 -0.1291 0.8695 0.0247 -11.250 -0.4103 0.04248 0.03949 -0.1338 0.8615 0.0251 -11.000 -0.3883 0.03954 0.03643 -0.1398 0.8545 0.0254 -10.750 -0.3624 0.03673 0.03353 -0.1462 0.8486 0.0259 -10.500 -0.3334 0.03415 0.03082 -0.1526 0.8429 0.0265 -10.250 -0.3007 0.03153 0.02804 -0.1597 0.8378 0.0270 -10.000 -0.2653 0.02929 0.02568 -0.1665 0.8337 0.0274 -9.750 -0.2275 0.02690 0.02312 -0.1737 0.8293 0.0280 -9.500 -0.1931 0.02563 0.02179 -0.1777 0.8250 0.0287 -9.250 -0.1572 0.02449 0.02060 -0.1820 0.8207 0.0292 -9.000 -0.1197 0.02326 0.01932 -0.1866 0.8175 0.0298 -8.750 -0.0820 0.02208 0.01806 -0.1910 0.8137 0.0305 -8.500 -0.0454 0.02111 0.01701 -0.1946 0.8098 0.0311 -8.250 -0.0092 0.02025 0.01604 -0.1979 0.8058 0.0316 -8.000 0.0282 0.01937 0.01506 -0.2016 0.8021 0.0321 -7.750 0.0617 0.01880 0.01446 -0.2034 0.7986 0.0330 -7.500 0.0967 0.01820 0.01384 -0.2058 0.7947 0.0337 -7.250 0.1319 0.01759 0.01319 -0.2083 0.7907 0.0344 -7.000 0.1669 0.01705 0.01257 -0.2107 0.7866 0.0351 -6.750 0.2020 0.01650 0.01198 -0.2130 0.7829 0.0359 -6.500 0.2371 0.01595 0.01140 -0.2152 0.7788 0.0367 -6.250 0.2717 0.01544 0.01083 -0.2173 0.7744 0.0374 -6.000 0.3071 0.01497 0.01029 -0.2195 0.7699 0.0385 -5.750 0.3430 0.01439 0.00968 -0.2220 0.7657 0.0396 -5.500 0.3783 0.01383 0.00909 -0.2243 0.7611 0.0407 -5.250 0.4131 0.01331 0.00851 -0.2264 0.7560 0.0419 -5.000 0.4469 0.01289 0.00801 -0.2281 0.7506 0.0431 -4.750 0.4837 0.01217 0.00723 -0.2308 0.7457 0.0449 -4.500 0.5190 0.01155 0.00656 -0.2330 0.7399 0.0469 -4.250 0.5523 0.01112 0.00605 -0.2345 0.7338 0.0489 -4.000 0.5849 0.01077 0.00564 -0.2358 0.7276 0.0505 -3.750 0.6205 0.01000 0.00479 -0.2381 0.7203 0.0547 -3.500 0.6521 0.00973 0.00444 -0.2390 0.7130 0.0580 -3.250 0.6846 0.00935 0.00401 -0.2402 0.7038 0.0636 -3.000 0.7154 0.00921 0.00378 -0.2408 0.6937 0.0681 -2.750 0.7470 0.00894 0.00344 -0.2417 0.6833 0.0787 -2.500 0.7817 0.00814 0.00281 -0.2439 0.6745 0.1827 -2.250 0.8121 0.00794 0.00271 -0.2446 0.6647 0.2586 -2.000 0.8414 0.00801 0.00276 -0.2447 0.6552 0.2709 -1.750 0.8701 0.00814 0.00282 -0.2447 0.6453 0.2786 -1.500 0.8990 0.00825 0.00287 -0.2447 0.6342 0.2840 -1.250 0.9275 0.00842 0.00300 -0.2447 0.6230 0.2896 -0.750 0.9848 0.00871 0.00317 -0.2446 0.6059 0.2961 -0.500 1.0138 0.00877 0.00321 -0.2447 0.5991 0.2991 -0.250 1.0424 0.00889 0.00331 -0.2447 0.5929 0.3016 0.000 1.0713 0.00899 0.00340 -0.2448 0.5868 0.3036 0.250 1.0996 0.00913 0.00351 -0.2448 0.5803 0.3060 0.500 1.1281 0.00927 0.00364 -0.2447 0.5745 0.3088 0.750 1.1567 0.00938 0.00373 -0.2448 0.5683 0.3108 1.000 1.1848 0.00952 0.00382 -0.2447 0.5618 0.3120 1.250 1.2137 0.00953 0.00382 -0.2449 0.5560 0.3141 1.500 1.2422 0.00959 0.00387 -0.2449 0.5495 0.3155 2.000 1.2985 0.00978 0.00405 -0.2449 0.5367 0.3180 2.250 1.3263 0.00992 0.00417 -0.2448 0.5295 0.3196 2.500 1.3539 0.01006 0.00430 -0.2447 0.5224 0.3214 2.750 1.3816 0.01018 0.00441 -0.2446 0.5144 0.3232 3.000 1.4088 0.01033 0.00453 -0.2445 0.5062 0.3245 3.250 1.4363 0.01045 0.00463 -0.2444 0.4974 0.3258 3.500 1.4630 0.01063 0.00476 -0.2441 0.4869 0.3269 3.750 1.4890 0.01085 0.00492 -0.2438 0.4741 0.3278 4.000 1.5157 0.01101 0.00505 -0.2435 0.4622 0.3287 4.250 1.5413 0.01121 0.00519 -0.2432 0.4462 0.3310 4.500 1.5655 0.01153 0.00543 -0.2425 0.4263 0.3324 4.750 1.5892 0.01189 0.00570 -0.2418 0.4070 0.3337 5.000 1.6121 0.01229 0.00600 -0.2409 0.3856 0.3351 5.250 1.6338 0.01275 0.00636 -0.2399 0.3621 0.3364 5.500 1.6539 0.01331 0.00677 -0.2385 0.3384 0.3378 5.750 1.6743 0.01380 0.00717 -0.2372 0.3181 0.3393 6.000 1.6942 0.01429 0.00758 -0.2358 0.3009 0.3408 6.250 1.7135 0.01478 0.00799 -0.2343 0.2861 0.3423 6.500 1.7313 0.01529 0.00842 -0.2325 0.2723 0.3436 6.750 1.7501 0.01571 0.00881 -0.2309 0.2622 0.3445 7.000 1.7677 0.01614 0.00921 -0.2291 0.2535 0.3459 7.250 1.7844 0.01652 0.00960 -0.2271 0.2465 0.3479 7.500 1.7953 0.01704 0.01011 -0.2240 0.2395 0.3492 7.750 1.8122 0.01748 0.01057 -0.2221 0.2339 0.3506 8.000 1.8270 0.01807 0.01116 -0.2199 0.2273 0.3520 8.250 1.8431 0.01861 0.01171 -0.2180 0.2217 0.3534 8.500 1.8587 0.01919 0.01230 -0.2160 0.2154 0.3549 8.750 1.8717 0.01994 0.01304 -0.2138 0.2076 0.3563 9.000 1.8856 0.02066 0.01375 -0.2117 0.1982 0.3578 9.250 1.8971 0.02154 0.01460 -0.2093 0.1864 0.3592 9.500 1.8985 0.02312 0.01599 -0.2056 0.1583 0.3603 9.750 1.8724 0.02670 0.01919 -0.1986 0.1038 0.3606 10.250 1.8447 0.03292 0.02504 -0.1892 0.0401 0.3615 10.500 1.8490 0.03473 0.02688 -0.1869 0.0348 0.3633 10.750 1.8546 0.03649 0.02867 -0.1848 0.0325 0.3648 11.000 1.8609 0.03822 0.03046 -0.1828 0.0308 0.3662 11.250 1.8692 0.03978 0.03210 -0.1811 0.0299 0.3675 11.500 1.8754 0.04157 0.03396 -0.1793 0.0289 0.3688 11.750 1.8803 0.04354 0.03598 -0.1774 0.0280 0.3701 12.000 1.8835 0.04573 0.03824 -0.1755 0.0269 0.3713 12.250 1.8851 0.04814 0.04073 -0.1737 0.0260 0.3726 12.500 1.8917 0.05008 0.04274 -0.1723 0.0255 0.3740 12.750 1.8972 0.05215 0.04488 -0.1708 0.0250 0.3753 13.000 1.9010 0.05445 0.04725 -0.1694 0.0244 0.3765 13.250 1.9042 0.05686 0.04974 -0.1680 0.0237 0.3775 13.500 1.9058 0.05952 0.05246 -0.1667 0.0231 0.3788 13.750 1.9043 0.06262 0.05564 -0.1654 0.0224 0.3806 14.000 1.8972 0.06644 0.05958 -0.1640 0.0217 0.3818 14.250 1.9002 0.06909 0.06231 -0.1631 0.0214 0.3832 14.500 1.9027 0.07181 0.06512 -0.1622 0.0211 0.3845 14.750 1.9037 0.07477 0.06816 -0.1613 0.0206 0.3859 15.000 1.9032 0.07796 0.07144 -0.1606 0.0202 0.3873 15.250 1.9022 0.08123 0.07479 -0.1599 0.0197 0.3886 15.500 1.9006 0.08459 0.07822 -0.1592 0.0193 0.3899 15.750 1.8962 0.08838 0.08208 -0.1587 0.0189 0.3911 16.000 1.8883 0.09272 0.08651 -0.1582 0.0184 0.3920